Afterburner

About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.

Control method of aircraft jet turbine engine

Abstract: FIELD: engine devices and pumps.SUBSTANCE: expected technical result is achieved by the fact that in the known method of controlling the aircraft jet turbine engine, which includes maintaining the preset rotational speeds and gas temperature behind the turbine by means of a regulator, depending on the air inlet temperature, according to the present invention, the regular regulation program conducts its tests in full afterburner mode (engine operation mode with maximum fuel consumption through afterburner collectors) with thrust measurement, then the regulator is adjusted to increase the rotors rotation speed and the gas temperature behind the turbine, not exceeding the maximum permissible values for this type of engine, until a predetermined thrust gain is reached, and regulator values are fixed, and if the predetermined thrust gain is not attained, the values of the regulator are also fixed for the maximum thrust gain, then, on the basis of the obtained data, an additional regulation program for rotors rotation frequencies and the gases temperature behind the turbine is made, it is installed into the engine regulator, then during engine operation, if it is necessary to increase the thrust in excess of the nominal modes, involve an additional program for regulating the rotors rotation frequencies and the gases temperature behind the turbine.EFFECT: possibility of increasing the thrust beyond the normal modes during the engine operation.2 tbl, 2 ex

Automotive fuel cell has afterburner chamber void filled with open pored silicon carbide foam ceramic foam block with glow plug ignition with regulated input of combustion gases

Abstract: An automotive fuel cell has an afterburner which processes residual gases arising from the reforming process and/or from a fuel cell operation. The afterburner has a jet (2) delivering fuel and residual gases to the combustion chamber (8) and an air supply. The combustion chamber has a void which especially is filled by an opened/pored ceramic foam block (4). The foam block is made in part or whole of silicon carbide and formed by reticulation. The foam block is electrically heated and in direct contact with the burner chamber wall, to which it surrenders heat. The foam block bears a catalytic coating of platinum. The afterburner further has an ignition system which is a heated helical wire (14) or glow plug. The ignition system is located between the ceramic block and jet, or within the foam block. The jet has a swirl nozzle or a multi-hole nozzle.

Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall

Abstract: Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.

Effect of Turbojet Compressor Coolants on Afterburner Combustion

Abstract: In the combined use of compressor coolant injection and afterburning as a means of achieving maximum thrust augmentation of a turbojet engine, the coolants investigated (water-alcohol mixture and liquid ammonia) reduced the combustion temperature and efficiency, and limits of stable combustion in the afterburner. The mechanism of this negative influence is related to the effect of water vapor and ammonia on the combustion propagation mechanism.

Jet turbine engine

Abstract: FIELD: engines and pumps.SUBSTANCE: jet turbine engine includes a housing, in which a turbine with an exhaust cone, a mixer, an afterburner duct and a nozzle are located in series. The exhaust cone includes cooled and non-cooled parts. The cooled part is provided with an annular channel formed with an inner shell and a perforated surface of the exhaust cone. The mixer forms together with the housing a cold air channel, and with the non-cooled part of the exhaust cone a hot air channel. The afterburner duct includes annular flame stabilisers. A small annular flame stabiliser is of a cooled type and installed so that it screens the non-cooled part of the exhaust cone on the nozzle side.EFFECT: invention allows reducing the infrared emission level of the jet turbine engine to rear semi-sphere of the aircraft and full pressure losses, and reducing overall dimensions and weight of the engine exhaust unit.5 cl, 3 dwg